Modular flight vehicle

ABSTRACT

The invention is a modular vehicle having an air vehicle that can be coupled to cargo containers, land vehicles, sea vehicles, medical transport modules, etc. In one embodiment the air vehicle has a plurality of propellers positioned around a main airframe, which can provide vertical thrust and/or horizontal thrust depending on the configuration. One or more of the propellers may be configured to tilt forward, backward, and/or side-to-side with respect to the airframe.

RELATED APPLICATIONS

The present application is a continuation of U.S. Utility applicationSer. No. 13/907,975, filed Jun. 3, 2013, now U.S. Pat. No. 9,108,728,which is a divisional of U.S. Utility application Ser. No. 12/070,669,filed Feb. 19, 2008, now U.S. Pat. No. 8,453,962, which claims priorityunder 35 U.S.C. § 119(e) to U.S. Provisional Application No. 60/901,809filed on Feb. 16, 2007, the entire contents of each of which are herebyincorporated by reference.

FIELD OF THE INVENTION

The present invention relates to flight vehicles, and more particularlyto flight vehicles configured to carry various payloads.

BACKGROUND OF THE INVENTION

Heavier-than-air flight vehicles have been known for that last 100 yearsor so, and include airplanes and helicopters. Such flight vehicles areused in many applications where speed is necessary to transport peopleand/or cargo to distant locations.

In many applications, it is desirable to transport people and/ormaterials to distant locations where the terrain is rugged andfacilities may be lacking. For example, in many military applicationstroops and equipment must be delivered rapidly to intercept enemytroops. The use of flight vehicles is often the quickest method totransport such troops and equipment.

While airplanes have excellent lifting capacity and altitudecapabilities, most airplanes lack vertical takeoff or landing (VTOL) oreven short takeoff or landing (STOL) capabilities, and they typicallyrequire a large open space for takeoff and landing. In many ruggedlanding sites, airplanes are not suitable.

Helicopters can land and take off vertically, and have exceptionalmaneuverability. Helicopters are sometimes subject to accidents andfailures, such as engine or rotor failures, which in some situationswill lead to a failure and loss of the helicopter. Helicopters also userotors (as opposed to propellers), which involve swash plates and othercomplicated mechanisms. Additionally, many helicopters have difficultyoperating at high altitudes.

What has been needed is a vehicle that can be easily delivered anddeployed for flight, with heavy lift and excellent flightcharacteristics even at high altitudes, that is adaptable to many uses.The current invention meets those needs.

SUMMARY OF THE INVENTION

The invention is a modular vehicle including an air vehicle and one ormore payloads, such as ground vehicles, cargo containers, etc. Thevehicle may be able to fly, set down and drive on land, and/or set downand cruise on or in water while also having vertical takeoff and landing(VTOL) or short takeoff and landing capabilities (STOL).

Embodiments of the present invention include a flight vehicle having amain airframe defining an airframe plane, a plurality of propellersextending on supports from the main airframe, with at least onepropeller of the first propeller subset of the plurality of thepropellers having a forward tilt angle from the airframe plane withrespect to the airframe front of about −15 to 15 degrees, or about zerodegrees, and with a second propeller subset including at least onepropeller having a forward tilt angle from the airframe plane of between60 and 95 degrees, or about 90 degrees. One or more propellers of thesecond propeller subset may be configured to be tilted forward from azero tilt angle to a 90 degree tilt angle. One or more of the propellersmay be configured to vary in height relative to the airframe.

A flight vehicle can include a propeller/engine assembly held to asupport arm by a holder configured to permit the propeller/engineassembly to tilt away from or toward the airframe forward axis. Thepropeller/engine assembly holder may permit the propeller/engineassembly to tilt away from or toward the airframe longitudinal axisresponsive to a moment applied to the propeller/engine assembly byrotation of the propeller, such as may be caused by uneven liftingforces on an advancing vs. retreating propeller blade with respect tothe direction of flight. A restraining mechanism, such as shock absorberor active tilt mechanism (such as an electric motor), may be included tooppose, effectuate, or otherwise control the sideways tilt of thepropeller engine assembly. A tilta tilt mechanism configured toeffectuate tilt the propeller/motor assembly away from or toward theairframe forward axis.

The invention includes a method of operating a flight vehicle having aplurality of propellers and an airframe, involving positioning each ofthe plurality of propellers with a tilt angle of approximately zero withrespect to the airframe plane; providing power to all of the pluralityof motors, wherein the power is sufficient to lift the air vehicle offof the ground so the vehicle is airborne; with the vehicle airborne,maintaining or increasing power to a first propeller subset comprisingone or more of the plurality of motors; with the vehicle airborne,reducing power to a second propeller subset comprising one or more ofthe plurality of motors, while simultaneously; with power reduced oreliminated to the second propeller subset, tilting one or more of thepropellers of the second propeller subset forward with respect to theairframe front to a tilt angle of between 60 and 95 degrees; and withthe one or more of the propellers of the second propeller subset tiltedforward with respect to the airframe front to a tilt angle of between 60and 95 degrees, increasing power to the second propeller subset. Afterincreasing power to the second propeller subset while tilted forward,power may be reduced and even eliminated to one or more propellers ofthe first propeller subset.

The propellers of the first subset of propellers may be positionedgenerally adjacent the airframe front and airframe back, and thepropellers of the second subset of propellers may be positionedgenerally between the first subset of propellers and/or between theairframe front and airframe back. The heights of one or more of thepropellers, including first and/or second subsets, may be varied, eitheron the ground or during flight.

The vehicle is configured to be folded into a more compact form forstorage and/or transport. The vehicle can be delivered to a desiredlocation via truck, ship, aircraft, etc., and can be deployed quicklyfor use. In an embodiment of the invention, the propellers are held onpropeller supports extending from the airframe. The propeller supportscan extend from the airframe at various angles and lengths, and can beconfigured to swing or otherwise move away from the airframe to adeployed (flight) configuration and back to a stowed (storage)configuration where the propeller supports and associated propellers(potentially including the engines) are stowed against and/or inside theairframe. Vertically standing pivot arms may used for stowing anddeploying the propeller supports, which may be a triangular, cantilever,or other type of extension used to support the engines from the airframecenter section during flight. Electric motors, possibly including anelectric clocking system, may used to properly position the propellersfor storage.

The rotating engine support arms can rotate either from actuators orgears etc and even manual means from ground units or personnel. The armslock with mechanisms either stowed or deployed but a safety feature canalso make the arm lift up or out of the way or even have the engine dropoff in an emergency which allows for another engine to rotate into thatarea and counter that asymmetrical thrust.

All or part of the vehicle can drive or fly or float, etc. The vehiclecan include different modular components. One component may provideflight capability, while another component may provide driving ormaneuverability on the ground or water, etc. The components can fly,drive, or float, etc. either together or as individual pieces

One embodiment of a ground vehicle includes a snow-cat type ofadaptation including a treaded track and/or skis. Wheels and floatscould also be applied to various components of the invention.

An air vehicle according to an embodiment of the invention includes aplurality of propellers extending from a main airframe. The air vehiclehas vertical takeoff and landing (VTOL) as well as short takeoff andlanding (STOL) capabilities. The air vehicle may have the ability tohave its propellers swing into a stowed position that makes a tightlycompact vehicle that can fit into an aircraft (such as a military C-5cargo plane), ship, or other transport vehicle. The air vehiclepropellers may be configured to rotate (manually or automatically) orotherwise extend outwardly to a deployed (flight) position, whereby thepropellers are in position to lift the air vehicle off the ground forflight.

The propellers of the invention may be ducted fans, shrouded propellers,bladed propellers, or other propeller assemblies. A bladed propeller mayinclude any number of blades, depending on the particular application.The engines can be attached directly to or even be internal of theairframe with a drive to each propeller, or the engines to eachpropeller can be adjacent to and/or even directly connected to thepropeller on the propeller support arms. The propeller can be directlysecured to the engine via a rigid and fixed drive shaft without clutchor other similar mechanism, so that the propeller RPMs will be the sameas the engine RPMs. The propeller/engine assembly may include a clutch,such that the propeller can remain still while the engine is running(i.e., at idle, etc.). The propellers can be variable-pitch propellers,such as electric variable-pitch propellers for atmospheric densitychanges, etc.

The propellers (possibly including attached engines and drive shafts)may be configured to cant front-to-back and/or side-to-side in order toeither turn the vehicle in the yaw axis, counter asymmetrical thrust incase of an engine out condition, tilt the aircraft in the air so thatthe main fuselage can remain more level, etc. The propellers may betilted in or opposite the direction of motion of the vehicle. Thepropeller support arms can be telescoping to allow for various propellersized and/or for repositioning of a propeller.

A vehicle according to the invention could be launched in variousmethods. The vehicle could launch in a STOL or VTOL technique from landor sea, or from platforms (such as buildings, movable platforms, orships) on land or sea. The vehicle could include a parachute and/orparafoil or similar device secured to the airframe in order to belaunched and/or delivered via air dropping (e.g., from a cargo planesuch as a military C-5 or C-130). A drogue chute could stabilize thefall, the engines could start to idle as the drogue chute is retrievedvia a mechanism, and the engines could then start to apply full power asthe drogue chute is retrieved. The vehicle could also be dropped withjust a streamer to stabilize the vehicle, and then start the motors oncestability is achieved. Even a freefall with no decelerator may work,with the propellers themselves providing stability and slowing the fallof the vehicle until the engines are fully started. The vehicle couldalso include an emergency parachute or similar device to be deployed incase of an emergency, such as loss of power to all engines. Theemergency parachute could be deployed using an explosive device thatthrows the parachute into a deployed configuration. A so-calledballistic parachute could be used as an emergency parachute.

The vehicle could be configured for delivery or even launch from atorpedo tube. For example, the diameter of a submarine missile tube isbetween 6′ and 7′ in diameter and 28 feet long, and a version of thisvehicle can fit in the missile tube and fold away safely for specialmissions.

The air vehicle may be configured with interchangeable components,including engines, propellers, and corresponding supports. This allowsdifferent components to be exchanged in a relatively rapid fashion forrepairs and/or different performance requirements. For example, a set ofshort propellers could be used for applications where rapid accelerationand high speed were desired for the air vehicle, with a set of longerpropellers replacing the shorter propellers for use in applicationswhere high lift and high altitude performance are desired for the airvehicle.

Large multi-engine versions can be made, with each propeller driven bynot just one but several engines. The added engines not only allow foradditional thrust but can also provide redundancy in case of engineloss/failure. The engines can be diesel, (including turbodiesel),electric, hybrid, hydrogen, and other fuel burning motors that turn thepropellers sufficiently to propel the aircraft with the payload throughthe air with good performance.

The air vehicle could be configured to connect with and lift a portablemedical treatment facility, such as the LSTAT used by the US Army whichis an enlarged medical litter that is essentially a small ICU configuredto hold not just a patient but also medical equipment and medicalpersonnel. Such a portable medical treatment facility could fit insideand/or be secured underneath (or to another portion of) an air vehicleof the invention. The air vehicle could be configured to accommodate themedical personnel inside the cockpit of the air vehicle, but stillprovide access to and from the portable medical treatment facility fromthe cockpit.

The vehicle may include lifting assemblies for lifting items from theground/water/etc. up to and airborne vehicle. In one such embodiment, alitter or net-like device is used to lift items up to the vehicle. Thenet may have a relatively rigid frame or be more sling-like, dependingon the particular application.

The vehicle can include external payloads in various forms. Externaldrop tanks configured to carry fuel for the air vehicle (or for deliveryto offsite location). Reserve fuel tanks can be located just above thedrop fuel tanks for emergency flight if any of the engines quit or isdamaged during the flight. Quick fuel dumps can also be done withoutlosing the fuel tanks. The reserve tank would still contain enough fuelto fly to a safe location for landing. The drop takes are below thereserve tanks since they may have to drop during flight. They can belocated almost anywhere on the vehicle including by the engines themselves. If the engines are internal to the aircraft then they can beeven there. To mate the Flight system to the Ground vehicle it ispreferred to place the fuel tanks on the lower sections and out sidesections of the vehicle, where the ground wheels will not affect theirplacement.

The air vehicle can be controlled by an onboard pilot or computersystem, or can be remotely controlled via computer and/or remote-locatedpilot. Traditional helicopter controls can be used in the interior ofthe vehicle for use by an operator along with the autonomous flightcontrols. There can be a collective and stick as with existinghelicopters to give control of the vehicle to an operator when needed.Note that the air vehicle can be remotely controlled, directlycontrolled from within the cockpit, or controlled by the autopilot. Asatellite link through Iridium and others may be useful.

The air vehicle will typically have advanced electronics and computercontrols to maintain stability of the vehicle in flight. Such advancedcontrols can be of particular importance in controlling and adjustingthe power from the large numbers of propellers and engines that may beinvolved. Many such control systems are already known in the art for usewith helicopters and other flight vehicles. Modern aircraft navigationsystems can work well with this vehicle. A neural net computer systemmay be employed. Vehicle stability can be provided by gyros located,e.g., on the centerline between engines that goes through the center ofgravity of the vehicle when it is empty. Gyros can be used on acenterline from the empty vehicle center of gravity and even from thefull vehicle center of gravity, depending on the need. At least one gyroper axis may be preferred, although at times only one gyro may be useddepending on the size and complexity of the vehicle. The gyrostabilization may be at least 70 cycles per second for updates to thethrottles to each engine, etc.

Navigation systems can include GPS systems and other modern navigationmethods. An autopilot can be used, including many of the helicopter-typestate of the art autopilots currently available, such as a Piccolo 2series autopilot when interfaced with neural net computer software likethe one that the Naval Research Laboratory has developed for theirSPIDER Helicopter. In addition to other navigation systems, an obstacleavoidance system such as a scanning laser system may be employed to findobstacles in the air vehicle flight path. Difficult-to-spot obstaclessuch as power lines, etc. may be located using map data, etc. Otheraircraft can be avoided through the use of transponder information, byreceiving secure data by friendly aircraft as to where they are by GPScoordinates, etc.

Vehicle sizes range from very small (e.g., nanorobot size) to verylarge. This vehicle can also be a toy that is sold to consumers. Thelarger versions may be configured to lift very large payloads, includingtanks, and also to be driven on highways when on the ground.

Due to issues with currently available vertical lift vehicles, a needexists for a vertical lift vehicle that has improved liftcharacteristics, reduced cost, and increased reliability. The presentinvention addresses these needs.

BRIEF DESCRIPTION OF THE DRAWINGS

FIG. 1 is a perspective view of a vehicle according to an embodiment ofthe invention;

FIGS. 2A, 2B, 2C, 2D, 2E, 2F, and 2G are front perspective, top, bottom,side, front, back, and back perspective views, respectively, of an airvehicle according to an embodiment of the invention;

FIGS. 2H-2I are close-up views of a landing support according to anembodiment of the invention;

FIGS. 3A through 3C are top, top (in cross-section), and perspectiveviews of the air vehicle from FIG. 2A showing various positions of theengines and propellers and support arms;

FIGS. 4A and 4B are side views, respectively, of a propeller support armassembly according to an embodiment of the invention;

FIG. 4C is a close-up top view, in cross section, of a portion of thepropeller support arm assembly of FIG. 4A;

FIGS. 5A and 5B are top and back views respectively of an engine andpropeller assembly and support in vertical lift configuration accordingto an embodiment of the invention;

FIGS. 5C and 5D are top and back views of the engine and propellerassembly and support of FIG. 5A in forward flight configuration;

FIGS. 6A-6C are back views of an engine and propeller assembly andsupport according to a further embodiment of the invention;

FIGS. 7A and 7B are top views of a flight vehicle according to anembodiment of the invention;

FIG. 8 is a perspective view, in partial cross section, of a fuel tankassembly of an air vehicle according to an embodiment of the invention;

FIG. 9A is a perspective view of an air vehicle carrying an externalpayload;

FIG. 9B is a side view of the external payload from FIG. 9A;

FIG. 10A is a perspective view of an air vehicle carrying a groundvehicle;

FIG. 10B is a perspective view of the ground vehicle from FIG. 10A;

FIGS. 10C and 10D are front and perspective views of a vehicle having aground vehicle and air vehicle and configured to be driven on theground;

FIGS. 11A-11C are perspective views of an air vehicle lowering a groundvehicle via cables;

FIGS. 12A-12C are side views of vehicles configured for carrying by anair vehicle according to an embodiment of the invention;

FIG. 13A is a perspective view of an air vehicle with aerial elevatorpreparing to lift a payload according to an embodiment of the invention;

FIG. 13B is a perspective view of the air vehicle with aerial elevatorof FIG. 12A lifting the payload;

FIG. 13C is a perspective view of the air vehicle with aerial elevatorof FIG. 12A with the payload lifted and secured to the exterior of theair vehicle;

FIG. 13D is a perspective view of an air vehicle with aerial elevatorwith a payload lifted and secured within the interior of the airvehicle;

FIGS. 14A-14C are perspective views of an air vehicle tethered with aground vehicle according to an embodiment of the invention;

FIG. 15 depicts a perspective view of an air vehicle with graspersaccording to an embodiment of the invention;

FIGS. 16A and 16B depict perspective and side view, respectively, of airvehicles with armor and gun mounting arrangements according to anembodiment of the invention;

FIG. 16C depicts a side view of an air vehicle with gun mount accordingto a further embodiment of the invention;

FIGS. 17A and 17B are side and perspective views, respectively, of aground vehicle loading a cargo module into an air vehicle according toan embodiment of the invention;

FIG. 17C is a side view of the cargo module and ground vehicle of FIGS.17A-17B secured to the air vehicle;

FIG. 18A is a perspective view of an air vehicle comprising flightcomponents releasably attached to a shipping container according to anembodiment of the invention;

FIG. 18B is a close-up view of a flight component of FIG. 18A;

FIG. 18C is a perspective view of an air vehicle comprising flightcomponents releasably attached to a shipping container according to afurther embodiment of the invention;

FIGS. 19A and 19B are perspective and side views respectively of aflight vehicle in a forward flight configuration according to anembodiment of the invention;

FIGS. 20A and 20B are perspective and (partial) top views, respectively,of an attachment frame according to an embodiment of the invention;

FIGS. 20C and 20D are close-up views of an attachment frame beingsecured to a ground vehicle according to an embodiment of the invention;

FIG. 20E is a side view depicting an air drop of an air vehicleaccording to an embodiment of the invention;

FIGS. 21A and 21B are perspective and side views, respectively, of anair vehicle according to an embodiment of the invention;

FIGS. 22A and 22B are top views of air vehicles according to embodimentsof the invention;

FIG. 22C is a side view of the air vehicle of FIG. 22 b;

FIGS. 23A and 23B are top and side views, respectively, of an airvehicle according to an embodiment of the invention;

FIGS. 24A and 24B are perspective views of an air vehicle according toan embodiment of the invention;

FIGS. 25A, 25B, and 25C are front, side, and perspective views,respectively, of an air vehicle according to an embodiment of theinvention; and

FIGS. 26A-26E are front, top (stored), top (deployed), perspective(vertical takeoff), and perspective (forward flight) views of variousconfigurations of an air vehicle according to an embodiment of theinvention.

DETAILED DESCRIPTION OF PREFERRED EMBODIMENTS

FIG. 1 depicts a vehicle 10 according the invention. The vehicle 12includes a transport module 14 in the form of a ground vehicle 16 matedto an air vehicle 20.

FIGS. 2A-2E depict an air vehicle 20 according to an embodiment of theinvention, comprising a main airframe 22 having a forward axis 23passing through its middle in back-to-front fashion. Eight (8)propellers 24 extend from the airframe 22 on propeller supports 26. Eachpropeller support 26 has a proximal end 28 secured to the main airframe22, and a distal end 30. In the particular embodiment depicted, eachpropeller 24 is linked to and individually powered by a devoted engine32, with a linked propeller 24 and engine 32 forming an engine-propellerassembly 34. One engine-propeller assembly 34 is positioned at thedistal end 30 of each propeller support 26. Note that theengine-propeller assemblies for use with the invention may havedifferent configurations, depending on the particular application. Inone embodiment, each of the engines 32 provides about 140 or morehorsepower, with each engine 32 driving a propeller 24 having an overalllength of about 7-9 feet. The propellers 24 may be configured to beeasily removed and replaced, either with identical propellers or withdifferent types of propellers, such as propellers which are longer orshorter, etc.

As shown most clearly in the top view of FIG. 2B, the propellers 24 arespaced around the main airframe 22, with four of the propellers 24extending from the airframe front 36 and four of the propellers 24extending from the airframe rear 38. Four of the propellers 24 extendfrom the airframe left side 40, while the other four propellers 24extend from the airframe right side 42. The propellers 24 and propellersupports 26 extend in pairs from the airframe corners 44 a, 44 b, 44 c,44 d. Different propellers 24 of the air vehicle 20 can rotate indifferent directions, depending on the particular application andincluding such variables as the spacing of the propellers, the totalnumber of propellers on a particular air vehicle, and othercharacteristics of a particular air vehicle, including the engines andpropellers thereof. In the particular embodiment of FIG. 2B, thepropellers 24 extending from the airframe left side 40 have a rotationaldirection 47 left in a generally counterclockwise fashion when viewedfrom above, while the propellers 24 extending from the airframe rightside 42 have a rotational direction 47 right in a generally clockwisefashion when viewed from above. With such rotations, the blades of eachpropeller 24 are in a forward motion with respect to the air vehicle 20when they are closest to the airframe 22, and are in a backward motionwith respect to the air vehicle 20 when they are furthest away from theairframe 22. Note that other rotation patterns are also within the scopeof the invention. For example, adjacent propellers may rotate inopposing directions, similar to the egg-beater style opposing rotationof the helicopter blades of a two-propeller Chinook helicopter.

As best seen in the side view of FIG. 2D, the propellers 24 arepositioned generally aligned in an air vehicle horizontal plane 46adjacent the airframe top 48, and are tilted slightly forward from theair vehicle horizontal plane 46 by a forward tilt angle 50, such as aforward tilt angle of zero to 5 degrees, with 3 degrees beingappropriate for some applications. The forward tilt angle 50 of eachpropeller 24 can vary (including variations from propeller topropeller), depending on the particular embodiment. In one embodiment,propellers 24 are generally fixed at a forward tilting angle 50 of aboutzero to 5 degrees. In another embodiment, the propellers 24 can beselectively rotated in flight (using a mechanical tilting mechanism suchas a hydraulic, electric, or other device or assembly) through varioustilt angles, including from horizontal to forward by about 90 degrees oreven backward by up to about 90 degrees (i.e., a forward tilt angle 50of −90 degrees). In other embodiment, some of the propellers have verysmall forward, or even zero, forward tilt angles, while other propellersare tilted forward at much greater angles.

Note that an air vehicle horizontal plane is defined as a plane passingthrough the air vehicle in a generally horizontal manner with respect tothe air vehicle, i.e., horizontal when the air vehicle is on the groundand/or when in a level configuration (e.g., in purely vertical flightmode).

Extending from the bottom 49 of the main airframe 22 are landingsupports 52 configured to support the weight of the air vehicle 20 whenit is resting on the ground. In the particular embodiment depicted, thelanding supports 52 include wheels 54 to permit the air vehicle 20 to berolled and/or driven on the ground. The wheels 54 may be powered and/orsteerable, or may be free moving, depending on the particularapplication. In other embodiments, the air vehicle 20 may include floatsfor landing on and/or cruising in a boat-like fashion on water, skis forlanding on and/or cruising on snow and/or ice, or other assemblies forlanding and/or traveling on various surfaces. The particular landingsupports 52 depicted in FIGS. 2A-2H are in their flight position, butare each configured to swing outward about an axis 56 to a landingposition, whereby the landing supports 52 extend from the sides of thevehicle, as depicted in the close-up views of FIGS. 2H-2I. The landingsupports 52 have a length 55, and in the particular embodiment depictedare configured to extend in length 55 from a shorter retracted (flight)configuration in FIG. 2H to a longer deployed (landing) configuration inFIG. 2I.

The landing supports 52 may have sufficient height 55 when deployed topermit a ground vehicle to be driven under the main airframe 22. Thelanding supports 52 may be extendable and/or retractable, and may beconfigured to telescope in length 55 and/or to swing or otherwise extendoutward from the main airframe 22. In some embodiments, the landingsupports 52 may include hydraulic, electric, and/or other extendingmechanisms to extend, retract, and/or otherwise reposition the landingsupports 52, and such extending mechanisms may have sufficient liftingcapacity to lift the air vehicle 20, when on the ground, from arelatively low height (such as may be desirable to directly load the airvehicle 20, such as through the rear door 48), to a height sufficientfor a ground vehicle to be driven thereunder.

Landing supports can also be secured to the engine/propeller supportsand/or to the engine/propeller assemblies. For example, engine/propellerassemblies could include wheels, floats, etc. extending beneath them toprovide increased stability in situations where an engine/propellerassembly might contact the ground, such as where the air vehicle islanding on uneven terrain and/or water. Such landing supports on theengine/propeller assemblies and/or supports could also facilitatemovement of the engine/propeller assemblies and/or supports whendetached from the air vehicle, such as where such assemblies are beingreplaced or repaired.

A cockpit 37 is in the front 36 of the air vehicle 20, from which apilot can control the air vehicle 20 in flight and on the ground. Thecockpit 37 may have a cover/windshield configured to swing outwardlyopen to act as a door through which the crew can access the vehicle. Asdepicted in the rear views of FIGS. 2F and 2G, the air vehicle 20 mayinclude a rear door 58, which in the particular embodiment depicted (ina closed configuration in FIG. 2F and an open configuration in FIG. 2G)opens by lowering and forming a ramp for loading materials in the airvehicle 20 through the airframe rear 38.

In the embodiment of FIG. 2A, the propellers 24 are directly powered byengines 32 directly secured thereto by simple drive shafts. However,various engines and engine assemblies can be used with the invention.The engines can be mounted at the end of supports along with propellers,as in the embodiment of FIG. 2A, or the engine or engines can be mountedelsewhere (such as in or on the main airframe) and connected to thepropellers via a drive shaft assembly.

The specific engine type and power to be used depends on the particularapplication, including the air vehicle size, number and size ofpropellers, desired flight characteristics such as lift and speed, etc.In one version of an air vehicle according to the invention, such as anair vehicle configured for transport in a C-130 cargo airplane, theengines are Meyer nutating, Hirth 2-cycle, or Thielert 4-cycle orsimilar engines, including engines that burn jet, diesel, heavy fuel,and/or gasoline and can each provide 110 to 150 horsepower. Such enginescan be linked to propellers having lengths of 7 feet to 21 feet. Othersizes and configuration are also within his scope of the invention,including very large vehicles with lifting capacities of 100,000 lbsusing 4000 horsepower turbine engines driving 80 foot propellers orrotors.

Alternate methods of power are also within the scope of the invention.For example, the propellers could be directly powered by electricmotors, with electricity provided by batteries and/or solar cells.Electricity could also be provided by a conventional engine thatconsumes fuel (e.g., gas, diesel, jet fuel, hydrogen, etc.) and acts asa generator to provide electricity to the electric motors and/orbatteries in a so-called “hybrid” arrangement. In a configuration usingelectric motors, during flight some of the propellers may not need to bepowered and the power thereto can be disconnected. Moreover, theseunpowered propellers may begin to autorotate, particularly when thevehicle is in forward flight. Such autorotation of a propeller orpropellers could cause a corresponding turning of the correspondingelectric motor(s), and this turning of the electric motor could be usedto act as a generator, thereby generating electricity which could be fedinto the batteries and/or into the other electric motors.

In one embodiment of the invention depicted in FIGS. 3A-3C, an airvehicle 20 has propellers 24 a-h positioned on supports 26 a-h. Thepropellers 24 a-d on the left side 40 of the airframe 22 are depicted inthe deployed (i.e., flight) configuration, wherein the supports 26 a-dare rotated away from the airframe 22 at angles 60 a-d therefrom. Thepropellers 24 e-h on the right side 42 of the airframe 22 are depictedin their stored configuration, with the supports 26 e-h folded againstthe airframe 22 (so that the angles 60 e-h are generally equal to aboutzero) and the propellers 24 e-h (which are two-bladed propellers in theparticular embodiment depicted) and engines 32 e-h aligned snuglyagainst the airframe 22 and to each other.

Note that the number of propellers and associated supports can vary, aswell as the attachment points. For example, while FIGS. 2A-2B depictsupports secured to the corners of the airframe, other supportattachment points are also within the scope of the invention. Forexample, supports could be secured to a more central portion of theairframe, including in the center of either side. Such supportattachment locations could facilitate repositioning of engine/propellerassemblies via variation of the associated angles by which the supportsare rotated away from the airframe (such as angles 60 a-d from FIG. 3A).

Various supports 26 for the propellers 24 are within the scope of theinvention, with FIG. 4A depicting one such embodiment. The support 26has an arm 70 having a distal end 72 having a support 74 configured tohold an engine/propeller assembly 34, and a proximal end 76 secured to atriangular truss assembly 78. The triangular truss assembly 78 includesan upper portion 80 secured to the main airframe 22 via an upperconnection 82 near the airframe top 48, and a lower portion 84 securedto the main airframe 22 via a lower connection 86.

The support 26 and/or engine 32 and/or propeller 24 may be configured tobe dropped from the air vehicle 20 in case of an emergency such as lossof engine power (such as due to mechanical failure) or fire on, damageto, or loss of an engine 32 and/or propeller 24 such as may be caused byenemy attack. In one such embodiment, the upper connection 82 isconfigured with a breakaway mechanism, such as a small explosiveconfigured to sever all or a portion of the upper connection 82, and thelower connection 86 can comprise a ball joint or similar connection. Inthe particular embodiment of FIGS. 4A-4C, the upper connection 82comprises a bracket 83 secured to a rod 85 that passes through a hole 87in the upper portion 80 of the triangular truss 78 of the support 26. Insuch an embodiment, severing the upper connection 82 permits the entiresupport 26 (potentially with attached engine 32 and propeller 24) tofall away and outward via gravity and the rotational moment about theball joint of the lower connection 86, as depicted in FIG. 4B. If thepropeller 24 is still generating lift sufficient to lift the support 26and propeller/engine assembly 34, the inner wall 89 of the bracket 83will prevent the triangular truss upper portion 80 from being pushedinwardly into the airframe 22

The propeller supports according to various embodiments may be able toextend in length, e.g., in telescopic fashion, during vehicle set-upand/or during flight. The propeller supports can and may be secured tovarious positions on the airframe, e.g., the center of a side, front, orback (instead of at the corners), etc.

It is known that for lifting propeller blades in helicopters and similarvehicles, when the helicopter is in forward motion the propeller bladescreate increased lift when in the forward portion of their rotation(i.e., sweeping forward with respect to the helicopter direction ofmovement), and create less lift when in the backward portion of theirrotation. The resulting unevenness in lift can cause a rotational momentto be created about the forward direction of movement of the airvehicle. To compensate for this unevenness in lift between the advancingand retreating propeller blade, one or more of the propellers 24 of anair vehicle of an embodiment of the invention, potentially including oneor more of the complete propeller and engine assemblies 34, may beconfigured to tilt from one side to another with respect to thedirection of flight 90 of the air vehicle 20. FIGS. 5A and 5B depictsuch a propeller 24 and engine 32, with the propeller and engineassembly 34 and propeller support 16 in vertical lift configuration. Inthe particular embodiment depicted, the propeller 24 rotates in aclockwise fashion when viewed from above to define a 360 degree rotation88, so that if this configuration is maintained when the vehicle shiftsto forward motion an advancing propeller blade 24 a (i.e., for aclockwise rotation the left-hand portion 88 left of its rotation 88 withrespect to the flight direction 90, where the blade is advancing withrespect to the flight direction 90) will create more lift than aretreating propeller blade 24 r (i.e., for a clockwise rotation a bladepassing through the right-hand portion 88 right of its rotation 88 withrespect to the flight direction 90, where the blade is retreating withrespect to the flight direction 90).

In the particular embodiment of FIGS. 5A and 5B, the engine 32 is heldat the distal end 30 of the propeller support 26 by a generally U-shapedpropeller/engine support 92 having a rod 94 passing between the ends 96thereof. The rod 92 defines a rotational axis 98 about which the entirepropeller/engine assembly 34 can rotate. The rotational axis 98 for thepropeller/engine assembly 34 is generally aligned with the flightdirection 90 of the air vehicle, except for any forward or backward tilt(such as the propeller tilt angle 50 depicted in FIG. 2D). A rotationalcontroller in the form of a shock absorber 100 extends from the engine32 to the propeller support 26, and serves to control and limit rotationof the propeller and engine assembly 34 about the rotational axis 98.The rotational controller could also be an active controller, such as aservo actuator that causes and/or prevents rotation of thepropeller/engine assembly 34 subject to commands from a control system.

Note that in the embodiment of FIGS. 5A and 5B, the propeller 24 ispositioned above the engine 32, and is directly connected to the engine32 via a drive shaft 102. The particular propeller 24 has blades each ofwhich are inclined slightly upward at an angle 104 from a plane 106perpendicular to the drive shaft 102. In purely vertical flight, thedrive shaft 102 (which aligns with to the rotational axis 108 of thepropeller 24) will typically be a purely vertical axis 110 (i.e., 90degrees from the horizontal) when viewed from behind the direction ofmovement as in FIG. 5B, so that the plane 106 will generally be parallelto the air vehicle plane 46.

FIGS. 5C and 5D depict a support 26 and propeller/engine assembly 34when the air vehicle is in forward flight. The uneven lifting forces onthe propeller 24 have created a rotational moment 112 (clockwise whenviewed from the rear as in FIG. 5D) about the propeller/engine assembly34, and the entire propeller/engine assembly 34 has slightly rotated byan assembly rotation angle 114, with the assembly rotation angle 114controlled and/or limited by a rotation controller such as the shockabsorber 100. The assembly rotation angle 114 causes the propeller 24 totilt slightly toward the right so that the propeller rotational axis 108is tilted to the right of the vertical axis 110. With this sidewaystilt, an advancing propeller blade 24 a in the forward sweep of itsrotation (88 left in FIG. 5C) is at a relatively large effective angle104 a from the air vehicle plane 46, while a retreating propeller blade24 r in the rearward portion of the rotation (88 right in FIG. 5C) is ata very small effective angle 104 b, and may even be generally parallelto, the air vehicle plane 46. The change in angles creates a reducedeffective lift area under advancing blade 24 a (i.e., on the left sidewhen viewed in FIG. 5D) but increased effective lift area under theretreating blade 24 r (i.e., on the right side in FIG. 5D). In purelyvertical flight, this unevenness in the propeller blade angles from leftto right with respect to the air vehicle plane 46 would create unevenlift, with less lift on the left than the advancing. However, whencombined with the uneven lift characteristics created by the forwardflight (i.e., advancing vs. retreating blades), the reduction/increasein effective lift area counters the increased/decreased lift caused bythe advancing vs. retreating blade, so that the resulting lift patternis generally equal throughout the blade sweep 88. The combination offorward flight with the uneven tilting of the engine/propeller assembly34 thus creates generally even lift characteristics, thus reducingstress on the propeller 24, engine 32, drive shaft 102, and othercomponents as well as reducing overall vibration.

FIGS. 5A-5D depicted a propeller 24 having blades with a fixed angle 104relative to a plane 106 perpendicular to the drive shaft 102. However,due to blade flexibility, a propeller 24 that is flat when not providinglift, as in FIG. 6A, may define a curved shape when rotating andsubjected to the lifting forces created thereby, as in FIG. 6B. Such apropeller 24 will define varying angles 104 a, 104 b, 104 c from theplane 106 along its length, with an angle 104 a of about zero atportions of the propeller 24 adjacent the drive shaft 102, but theangles 104 b, 104 c will steadily increase for portions of the blade 24that are further from the drive shaft 102. However, in purely verticalflight the angles 104 a, 104 b, 104 c will typically be equal from theleft side to the right side, as depicted in FIG. 6C. As with arotational propeller/engine assembly support such as that of FIGS.5A-5D, a curved propeller will also achieve a generally balanced liftpattern in response to rotation of the propeller and engine assembly, asdepicted in FIG. 6C. By tilting the propeller rotational axis 108 to theright (when viewed from behind as in FIG. 6C), the result is increasedangles between the advancing blade 24 a and the air vehicle plane 46,and decreased angles between the retreating blade 24 r and the airvehicle plane. The change in angles creates a reduced effective liftarea under advancing blade 24 a (i.e., on the left side when viewed inFIG. 6C) but increased effective lift area under the retreating blade 24r (i.e., on the right side). The reduction/increase in effective liftarea counters the increased/decreased lift caused by the advancing vs.retreating blade, so that the resulting lift pattern is generally equalthroughout the blade sweep.

The forward tilt angle (i.e., angle 50 from FIG. 2D) and/or sidewaysangle (i.e., angle 114 from FIGS. 5D and 6C) of a propeller 24 can bevaried using various techniques. For example, an electric motor,hydraulic system, or other mechanism could be used to tilt theengine/propeller assembly 34 (or just the propeller 24 itself), and/orall or a portion of the propeller support 26. As one example, one ormore connections by which a propeller support is secured to the airframecould be moved (i.e., the upper connection moved forward with respect tothe airframe, and/or the lower connection moved backward with respect tothe airframe) in order to tilt the propeller support and thereby tiltthe propeller forward. Reversing these movements could tilt thepropeller backward. In another example, an upper connection could bemoved outward while the lower connection could be moved inward, therebytilting the propeller support outward and thereby tilting the propelleroutward. Reversing these movements could tilt the propeller inward. Notethat the above connection movements may also be used, either alone or incombination with other devices and/or configuration changes, to raise orlower supports, engines, and/or propellers with respect to the airframe.The propeller support could be secured to the airframe via a bracket,and the bracket could be rotated or otherwise moved (via motors,hydraulics, etc.) to reposition the propeller support and therebyreposition the propeller angle(s) or height, etc.

While two-bladed propellers have been depicted herein, the invention isnot limited so such propellers. While two-bladed propellers may haveadvantages for stowing, manufacture, and/or travel, propellers with anynumber of blades can be used with the invention. The propellers may beconfigured to store in different ways. For example, they may fold alongone or more sides, front, back, top, or bottom of the vehicle, or beconfigured for partial or complete disconnect/reconnect from the vehiclefor storage/shipping and/or propeller exchange. Propellers may be ableto rotate from their deployed (flight) position to the stowed position,and vice-versa, either manually or via electric, hydraulic, mechanical,etc. methods.

The support angles 60 a-h of the various propeller supports 26 a-h canvary according to the particular application, including the generallyair vehicle configuration, number of propellers, load capabilities, etc.In the embodiment depicted in FIG. 7A, in flight configuration thesupports 26 a, 26 d, 26 e, and 26 h holding the front-most and rear-mostengine/propeller assemblies 34 a, 34 d, 34 e, 34 h extend at angles 60a, 60 d, 60 e, and 60 h of about 150 to 170 degrees, and the supports 26c-f supporting the central propellers 24 c-f extend at somewhat smallerangles 60 b-c, 60 f-g of about 60 to 80 degrees.

The supports 26 a-h may be configured so that the support angles 60 a-hcan be varied in flight, so that one or more of the supports 26 a-h canbe angled outward or inward to reposition the correspondingengine/propeller assemblies 34 a-h to compensate for center of gravitychanges, changes in thrust from various engines, loss of one or moreengines, and/or for other reasons necessary to enhance the flightcapabilities of the air vehicle 20. In one embodiment, one or moresupports 26 a-h can change their support angles 60 a-h in flight tocompensate for different weight balances and centers of gravity, and/orto compensate for loss of one or more engine/propeller assemblies 34 a-h(including loss of use thereof). For example, FIG. 7B depicts the flightvehicle of FIG. 7A having lost two engine/propeller assemblies 34 c-d,but with other engine/propeller assemblies 34 a-b, 34 g-h repositionedto compensate for the propeller losses. The supports 26 a-b, 26 g-h havebeen changed in their angles 60 a-b, 60 g-h to repositionengine/propeller assemblies 34 a-b, 34 g-h, with angles 60 a, 60 b beingdecreased and angles 60 g, 60 h being increased. The new propellerpositions compensate for the propeller loss, and further compensationcan be provided by adjusting thrust from different propellers, adjustingthe center of gravity via methods such as moving fuel from tanks fromside-to-side and/or front-to back and/or vice-versa, etc.

In one embodiment, the air vehicle 20 includes an active flight controlsystem that constantly monitors the flight characteristics, includingcenter of gravity, thrust from each propeller 24 a-h, power from eachengine 32 a-h, air vehicle speed and attitude, etc., and automaticallyadjusts one or more of the propeller forward tilt angles 50 a-h,propeller assembly side-to-side angles 114, and/or support angles 60a-60 h in order to reposition one or more of the propellers 24 a-h tomaximize the flight performance, including such factors as lift, fuelefficiency, etc. The flight control system may also adjust propellerposition, engine power (and hence propeller thrust), and center ofgravity (via fuel movement, etc.) to compensate for various factors suchas loss of one or more engines and/or propellers. When the vehicle isready to lift off, the active flight control system can adjust the RPMsof each engine via throttle controls in order to balance the thrust fromthe engines with respect to the center of gravity of the vehicle. If thecenter of gravity is off-center, the air vehicle can compensate byadjusting engine power (thereby adjusting propeller thrust) and also bytransferring fuel between different fuel tanks.

FIG. 8 depicts a fuel tank assembly 120 of an air vehicle 20, withmultiple fuel tanks 122 positioned in the vehicle. The fuel tanks 122are generally vertical in shape in order to minimize sloshing of thecontents, which could impact center of gravity and otherwise complicateflight characteristics of the air vehicle. Tank-to-tank fuel transferlines 124 permit rapid and effective fuel between tanks 122 in order toeven out the amount of fuel in each tank, balance the center-of-gravity,and/or for other purposes. Fuel transfer pumps 126 control the movementof fuel between fuel tanks 122. Fuel lines 128 lead from the fuel tanks122 through the supports 26 to the engines 32. Fuel can be fed to theengines via pumps and/or other methods (such as gravity, etc.),depending on the particular embodiment.

The air vehicle 20 may be configured to have fuel drop tanks 130 securedthereto. In the particular embodiment depicted, fuel drop tanks 130 arepositioned on either side of the vehicle, generally toward the center ofeach side and low on the vehicle. The fuel drop tanks 130 provide extrarange to the air vehicle 20. The drop tanks 130 are attached viaconnectors, with drop tank fuel lines configured to transfer fuel fromthe drop tanks 134 to the onboard fuel tanks 122 and/or directly to theengines 32. Pumps may be used to control such fuel transfer.

The drop tanks 130 may be configured for easy connection anddisconnection from the air vehicle 20. For example,quick-connect/disconnect assemblies may be used for quick connection anddisconnection of the drop tank fuel lines, and such assemblies may alsobe configured to be self-sealing. The drop tank connectors 132 may beconfigured for rapid disconnect during normal operations (e.g., loadingand unloading, etc.) and/or for dropping (e.g., via explosives or otherrapid disconnect devices) of the drop tanks 130, such as where a droptank 130 is empty of fuel and it is desirable to drop the drop tank 130.The drop tanks 130 can be dropped in flight or on the ground.

Air vehicles according to the invention may also include fuel lines andconnections to transfer fuel between a transport module, such as aground vehicle, to the air vehicle, or vice versa. The air vehicle willtypically include one or more gas fuel openings through which fuel canbe added in the traditional manner (e.g., from a traditional gas pumpsuch as found at gas stations). The air vehicle may be configured toautomatically transfer fuel to and/or from a transport module whenavailable. The air vehicle may also include in-air refueling devices topermit the air vehicle to be refueled in flight by an airborne tankerairplane or other airborne refueling platform.

FIG. 9A depicts an embodiment of a vehicle 10, where an air vehicle 20is carrying a transport module 12 in the form of a cargo module 140. Thecargo module 140, depicted alone in FIG. 9B, is configured be secured tothe underside 49 of the air vehicle 20. The cargo module 140 includesone or more doors 142 through which cargo can be loaded, and includesconnectors 144 configured to be mated to corresponding connectors on theair vehicle 20.

A vehicle 10 may include a transport module 12 in the form of a groundvehicle 14, such as that depicted in FIGS. 10A-10B. The ground vehicle14 is configured to drive on land via wheels 150. The ground vehicle 14includes connectors 152 configured to be mated to correspondingconnectors on the air vehicle 20. The particular ground vehicle 14depicted includes a rear cargo area 154 and a front cockpit 156 fromwhich a driver can control the vehicle, which may be accomplished usingtraditional ground vehicle controls (e.g., steering wheel, gas pedal,brake, etc.).

Note that in addition to or in lieu of wheels, a ground vehicle 14 orother transport module may include skis, skids, tank-like tracks, and/orother drive devices, depending on the particular application (includingthe terrain over which the ground vehicle is anticipated to operate). Inother embodiments, the vehicle or other transport module may includefloats for landing on and/or cruising in a boat-like fashion on water.

The vehicle 10 when on the ground can be driven using the ground vehicle14, with the air vehicle 20 secured to the top thereof as depicted inFIGS. 10C-10D. With the vehicle 10 is landed on the ground, theengine/propeller assemblies 34 and struts 26 can be retracted and foldedagainst/inside the air vehicle 20, and the air vehicle supports 52 canbe retracted (if not already retracted prior to landing) so that thewheels 150 of the ground vehicle 14 carry the entire weight of thevehicle 10, including the weight of the air vehicle 20 and groundvehicle 14. Controlling the driving of the entire vehicle 10 over theground can be accomplished via the ground vehicle cockpit 156 or fromthe air vehicle cockpit 36, with controls in either cockpit 156, 37configured to control (through direct connections, wireless, etc.) thepower to and steering of the ground vehicle wheels 150.

A transport module 12 such as a ground vehicle 14 can deposited onto theground or other surface by having the air vehicle 20 (with groundvehicle 14 attached) land on the ground or other surface and thenrelease the ground vehicle 14 therefrom. The transport module 12 cansimilarly be removed from the surface by securing the air vehicle 20 tothe transport module 12/ground vehicle 14 when on the ground, and thenlifting off the combined vehicle 10 using the air vehicle 20 to directlylift the transport module 12/ground vehicle 14. In another embodimentdepicted in FIGS. 11A-11C, a transport module 12 in the form of a groundvehicle 14 is lowered onto the surface from an airborne air vehicle 20using cables 158 (powered by winches or other reeling devices), so thatthe air vehicle 20 remains airborne at all times during landing of theground vehicle 14. The process can be reversed to lift the groundvehicle 14 up to the airborne air vehicle 20, with the cables 158 andwinches used to lift the ground vehicle 14. The cables 158 are securedto the corners of the ground vehicle 14 in order to provide betterbalance when lifting and/or lowering the ground vehicle 14. The cablescan also be used to guide the air vehicle 20 to a landing on top of asurface-based transport module 12 such as the ground vehicle 14, whereinone or more of the cables can be winched in to draw the air vehicle 20down onto the top of the ground vehicle 14.

A transport module 12 may be an amphibious vehicle 160 configured forcrossing land and water, as depicted in FIG. 12A. The amphibious vehicle160 includes a generally boat-like hull 162 and has sufficient buoyancyto float in water. A ground drive system in the form of multipleinflated wheels 164 (which also provide buoyancy) is used to drive theamphibious vehicle when on land. A water drive system in the form of oneor more propellers 166 provides forward thrust when in water. Note thatother types of ground and water drive systems are also within the scopeof the invention, including skis, skids, tank-like tracks, water-jetpropulsion, rudders, and/or other drive and/or steering devices. Theamphibious vehicle 160 includes connectors 168 configured to be mated tocorresponding connectors on the air vehicle 20. The amphibious vehicle160 can include controls, including a steering wheel 170, as well as awindshield 172 and one or more seats 174. All elements that extend abovethe top 176 of the amphibious vehicle 160 may be configured to fold downbelow the top in order for the amphibious vehicle 160 to be secured tothe air vehicle 20.

FIG. 12B depicts a boat 180 configured for carrying by an air vehicle.The boat 180 includes a hull 182, propulsion system in the form of oneor more propellers 184, and a rudder 186. Note that other propulsion andcontrol systems could also be used, including jet propulsion, bow/rearthrusters, etc. Connectors 188 are configured to mate with connectors onthe air vehicle. A windshield 190, steering wheel 192, and seats 194 areconfigured to fold or otherwise drop below the boat top 196 tofacilitate securing the boat 180 to an air vehicle.

FIG. 12C is a side view of a submersible 200 configured for carrying byan air vehicle. The submersible 200 includes a hull 202, propeller(s)204, and rudder 206. Connectors 208 are configured to mate withcorresponding connectors on the air vehicle, and the submersible'sconnectors 208 may be configured to fold or otherwise retract into thehull after submersible deployment in order to reduce drag on thesubmersible 200 when submerged.

A vehicle 10 may include an aerial elevator 210 configured to lift apayload 212 to the in-flight air vehicle 20. As depicted in FIGS.13A-13B, an aerial elevator includes a frame 214 secured at its corners216 to lift lines 218. Winches 220 or other hoisting devices are used tolet out and/or pull in the lift lines 218 and thereby lower or raise theframe 214.

The frame 214 may be a generally rigid structure, which may preventunwanted movement of lift lines 218 that might occur of the lift lines218 were unattached to any structure at their lower ends as they werelowered. The frame 214 can include connectors configured to be securedto the payload 212, such as by being mated to corresponding connectorson the payload 212. The frame 214 may also include connectors configuredto be secured to the air vehicle 20.

In FIG. 13A, the frame 214 is being lowered toward the payload 212. Theframe 214 is then connected to the payload 212 and the frame 214 withattached payload 212 is lifted, as depicted in FIG. 13B, which can beaccomplished by using the winches 220 to reel in the lines 218. Once theframe 214 is fully lifted to the underside 49 of the air vehicle 20, theframe 214 can be secured to the air vehicle 20, thereby securing thepayload 212 to the air vehicle 20, as depicted in FIG. 13C, with thepayload 212 secured to the underside 49 of the air vehicle 20.Alternatively, the payload 212 could be lifted up entirely (orpartially) within the air vehicle 20 itself, as depicted in FIG. 13D.

FIG. 14A depicts an air vehicle 20 in flight but tethered to a groundvehicle 14 according to an embodiment of the invention. The tether line230 has a lower portion 232 secured to a hook 234 or other connection ona landing pad 236 on the ground vehicle 14. The landing pad 236 includesextendable portions 238 that project from the sides of the groundvehicle 14. At the air vehicle 20, the tether line 230 extends from awinch or other reel device configured to pull in and let out the tetherline 230.

The tether line 230 can be carried on the air vehicle 20, and then thedistal portion 232 thereof dropped to the ground vehicle 14 to besecured to the hook 234. The winch can then be used to pull the airvehicle 20 down onto the landing pad 236, with the end result being theair vehicle 20 is on the landing pad 236 and secured thereto via thetether line 230, as depicted in FIG. 14B. With the air vehicle 20secured to the landing pad 236, the engine/propeller assemblies 34 canbe folded into the sides of the air vehicle 20, and the ground vehicle14 can drive with the air vehicle 20 secured to the top thereof.

The tether 230 can be used to assist in guiding the air vehicle 20 toland on the ground vehicle 14 (or on other desired locations, such as ona ship, narrow ledge, etc.). The tether 230 could also be used to liftthe ground vehicle 14 or other module, either by: winching the groundvehicle 14 via the tether 230 and winch/reel up to an airborne airvehicle 20; or securing the tether 230 to the ground vehicle 14 andusing the air vehicle propellers 24 to lift the air vehicle 20 andground vehicle 14, either by first landing the air vehicle 20 andsecuring it tightly via the tether 230 to the ground vehicle 14 (so thatthe ground vehicle 14 is held tightly to the air vehicle 20), or withoutlanding the air vehicle 20 on the ground vehicle 14 so that the groundvehicle 14 will hang some distance below the air vehicle 20 by a sectionof the tether line 230.

FIG. 15 depicts an air vehicle 20 with graspers 240 extending from theairframe 22. The graspers 240 include arms 242 with hands 244 at theends thereof. The graspers 240 can be used to grasp and/or releaseobjects, including transport modules, and can be controlled from thecockpit 37, via remote control, etc.

FIGS. 16A and 16B show an air vehicle 20 having armor 248 secured to thesides and bottom thereof. Guns 250 are also provided to extend from thefront and sides of the air vehicle 20. Two turret-style guns 252 aresecured to the air vehicle bottom 49, while an extendable gun 254 andextendable rocket launcher 256 are positioned on the top 48 of the airvehicle 20. The arms can be controlled from the cockpit 37 or asotherwise desired for a particular application.

FIG. 16C depicts a further embodiment of an air vehicle 20, with anextendable gun turret-style gun 252 secured to an elongate arm 251. Theelongate arm 251 is secured to the airframe 22 via a pivot 253 securedto a base form 255 that can rotate about an axis 257 on the top 48 ofthe airframe 22 adjacent the front 36 thereof. The turret-style gun 252can rotate about a first axis 259, and also swing up or down for stowingvia a hinge 249 that secures the turret-style gun 252 to the elongatearm 251. As depicted in FIG. 16C, the turret-style gun 252 can bepositioned above the airframe 22, then rotated over the airframe front36 to a position below the airframe 22, and moved to a stowedconfiguration along the top 48 of the airframe 22

FIGS. 17A-17C depict an air vehicle 20 having a rear cargo area 260 thatcan be open at the air vehicle bottom 49 and at the air vehicle back 38so that a cargo module 262 can be delivered therein by driving a groundvehicle 14 directly into position beneath the air vehicle 20. Asdepicted in FIGS. 17A and 17B, the cargo module 262 is positioned on topof the ground vehicle 14, and the ground vehicle 14 is driven toward theair vehicle 20 by approaching the air vehicle 20 from the back 38. Asdepicted in FIG. 17C, the ground vehicle 14 is driven underneath the airvehicle 20 until the cargo module 262 is positioned inside the rearcargo area 260 of the air vehicle 20. At this point, the cargo module262 can be secured directly into the rear cargo area 260 and the groundvehicle 14 can be driven away (or simply left behind when the airvehicle 20 takes off), or the ground vehicle 14 can be secured to theair vehicle 20 so that the ground vehicle 14 is delivered to thedeployment site along with the cargo module 262.

FIG. 18A depicts an air vehicle 20 including flight components 270releasably attached to a shipping container 272 at the corners 274thereof. The shipping container 272 can be a standard shippingcontainer, and the flight components 270 include a base frame 276 havingconnectors configured to secure to standard connectors of the shippingcontainer 272. Each flight component 270 comprises two engine/propellerassemblies 278 secured to two supports 280, and also includes one ormore fuel tanks 282. A flight control system 284 is also secured to theshipping container 280, and communicates with the flight components viawires 286 and/or wireless connections. The flight control system 284 cancontrol the flight by adjusting engine RPMs/propeller thrust,repositioning propellers/supports at different angles, and/or anglingpropellers side-to-side and/or front-to-back. An individual flightcomponent 270 is depicted by itself in FIG. 18B. Note that a flightcontrol system could be positioned on or in one or more of theindividual flight components, with different flight control systems fromdifferent flight components communicating (vie wires or wireless) tocoordinate control, so that the different flight control systemseffectively act as a single flight control system that controls theflight of the entire air vehicle.

FIG. 18C is another embodiment of an air vehicle 20 that can act as ashipping container transport system, but where each flight component 270comprises a base frame 276 and four engine/propeller assemblies 278 aswell as a flight control system 284 and a cockpit 288 in which a pilotcan sit to control the flight component 270 and/or air vehicle 20 (whenthe flight component is attached thereto). Each flight component 270 canbe flown by itself so that it can land and take off from a shippingcontainer 272 and other positions. With two flight components 270secured to a shipping container 272 (which in the particular embodimentof FIG. 18C involves slipping a flight component base frame 276 over anend of the container 272), the flight control systems 284 of each flightcomponent communicate with each other to coordinate the actions of eachflight component 270 and its associated engine/propeller assemblies 278to lift and transport the shipping container 272 to a desired location.

Individual flight components for moving a shipping container, such asdepicted in FIGS. 18A-18C, could include any number of propellers,engines, engine/propeller assemblies, flight control systems, etc.Flight components could be configured so that a single flight componentcould transport a shipping container without assistance from otherflight components, and/or multiple flight components could be secured toa container for transport thereof.

Enhanced flight performance in forward horizontal flight can be achievedby making changes to propeller position and/or power. While in verticaltake-off mode it may be desirable for all propellers to be essentiallyplanar with the horizontal, in forward flight one or more of thepropellers may be angled forward and/or power may be increased to somepropellers and/or reduced or even eliminated to other propellers. FIGS.19A and 19B depict an air vehicle 20 (similar to that depicted in FIG.2A) in a forward flight configuration, wherein the front-most propellerset 24 a, 24 e, front central propeller set 24 b, 24 f, and rear-mostpropeller set 24 d, 24 h are each tilted slightly forward by an angle114 and at generally the same heights with respect to the airframe 22.However, the rear central propeller set 24 c, 24 g has been movedsubstantially, so that the propellers 24 c, 24 g are at forward tiltangles 114 c, 114 g of about 90 degrees. The associated propeller/engineassemblies 34 c, 34 g have been lowered with respect to the airframe 22,which was achieved by lowering the supports 26 c, 26 g and also byrotating the propeller/engine assemblies 34 a, 34 g forward. Note thatadditional propellers, such as the front central propeller set 24 b, 24f, could also be rotated forward and/or lowered to achieve even greaterspeeds. Depending on the particular application, including the liftcharacteristics of the airframe and propellers, etc.), power could bediscontinued the front-most and rear-most propellers during forwardflight, and these propellers could be allowed to autorotate in order togenerate sufficient lift to maintain the vehicle at a desired altitude.

To transition between vertical take-off mode and horizontal flight,power to the rear central propellers 24 c, 24 g could be discontinued toprevent tilt propeller transition problems that might occur with poweredpropellers. The now-unpowered propellers 24 c, 24 g could then be tiltedforward to the desired angle (e.g., 90 degrees), and power restored tothe propellers 24 c, 24 g to provide forward thrust for forward flight.Power to the other (i.e., vertical lift) propellers could be reduced oreven eliminated, with the forward-facing propellers 24 c, 24 g providingmost of the power for forward flight and the other propellers 24 a, 24b, 24 d, 24 e, 24 f, 24 h providing lift either via direct power orautorotation.

Other repositioning of the propellers is also within the scope of theinvention. For example, propellers could be repositioned up and down (orin and out), including above and/or below the airframe, to achieveimproved aerodynamic performance. Propellers to which power has beeneliminated may be secured in a fixed position (such as a positiongenerally parallel to the direction of forward flight in order tominimize drag), or may be permitted to autorotate (in which case theywill typically generate some lift). A more aerodynamically efficientshell could be used for and/or with the airframe to give improvedperformance.

FIGS. 20A and 20B depict a frame 300 configured for attachment to atransport module such as a ground vehicle 14. The frame 300, which couldbe incorporated into a bottom structure of an airframe, includes a mainU-shaped body 302 and a back portion 304, with the back portion 304configured to be swung away from the main U-shaped body 302 for directaccess across the resulting back opening 306. The frame 300 includesconnectors 308 adjacent the frame corners and mid-portion in theembodiment of FIGS. 20A and 20B. The connectors 308 are depicted inclose-up in FIGS. 20C (engaging) and 20D (locked), and configured tomate with corresponding connectors 152 of the ground vehicle 14. In theparticular embodiment depicted, each frame connector 308 has a recess310 configured to receive a ground vehicle connector 152. A lockingmember 312 slides across the recess 310 and engages the ground vehicleconnector 152 to secure the ground vehicle 14 to the frame 300, asdepicted in FIG. 20D.

FIG. 20E depicts a cargo plane 320 delivering an air vehicle 20 using anair drop approach. The air vehicle 20 a is depicted in various states ofdeployment as 20 a, 20 b, 20 c, 20 dm 20 e, and 20 f. The air vehicle 20a is depicted just after having been dropped, with a parachute 322 abeginning to deploy. Air vehicle 20 b has parachute 322 b in a furtherstate of deployment. Parachute 322 c has fully stabilized air vehicle 20c, which is in the process of deploying its engine/rotor assemblies 34.Air vehicle 20 d is free of its parachute and is in flight via power tothe rotors 24.

FIGS. 21A and 21B depict a heavy lift version of an air vehicle 20,having separate decks inside configured to receive equipment andpersonnel.

FIGS. 22A-22C depict a further embodiment of an invention, whereinpropeller or ducted fan systems operate and hold an aircraft 340 instable flight for vertical takeoff and landing and other maneuvering.Different variations of the aircraft 340 are depicted in FIGS. 22A and22B. The propellers or ducted fans 341 are positioned generally equallyabout the center of gravity 342, and are covered by doors which can opento provide vertical thrust, and remain closed during horizontal flight.The aircraft has a front 343. A rear directed engine (or ducting todirect propeller/ducted fans rearward) propels the aircraft inhorizontal flight.

FIGS. 23A and 23B depict a further embodiment of an invention, whereinan air vehicle 350 is configured to drive on the ground in a foldedconfiguration (depicted in FIG. 23A) via wheels 352 extending below toprovide steering and/or power. The wheels may be powered from enginesdriving one or more of the propellers 356, 360. The air vehicle 350 hasa folded width 354 that permits it to drive down city streets. Fourpropellers 356 are positioned on outward pontoons 358, and areconfigured to provide vertical thrust for VTOL and/or STOL operations. Arear propeller 360 provides forward thrust for horizontal flight and/ordriving on the ground. The wings 362 can fold out for flight or fold infor storage and/or ground travel. When in vertical flight, power to thepropellers 356 can be reduced and/or eliminated, and/or the propellerscan be locked in a position generally parallel to the direction oftravel (which would typically be parallel to the forward axis 364 of theaircraft). The engines powering the vertical takeoff propellers could beelectric, with batteries in the pontoons 358, and the other propeller(s)360 could be powered by a more traditional fuel-driven engine thatdrives the propeller(s) 360 and also charges the batteries that provideelectricity to drive the vertical takeoff propellers.

FIGS. 24A and 24B depict an air vehicle 370 having a flightconfiguration (FIG. 24A) and ground configuration (FIG. 24B). The airvehicle 370 has an upper set of propellers (or ducted fans) 372configured to rotate to be positioned over the lower set of propellers(or ducted fans) 374 when in the ground configuration. In the groundconfiguration, the air vehicle 370 can travel down highways and possiblyeven hover for short hops. A separate engine can provide power to theground wheels 376 or use one of the air vehicle motors. This vehicle canbe ducted fan or propeller driven, and may have a similar verticaltakeoff stability system as other flight vehicles described herein. Thepassengers and drivers sit in the middle section 378. The two upperpropellers 372 can rotate from the ground configuration by about 90degrees so the upper propellers 372 extend out from the sides of the airvehicle 370, thus putting the air vehicle 370 in the flightconfiguration.

FIGS. 25A-25C depict an embodiment of a flight vehicle 380 that can belaunched from a torpedo or missile launch tube 382 as well as beingground and air launched. FIGS. 25A-25B depict the flight vehicle 380stowed in a folded configuration (with wings and tail assembly foldedup) within a missile launch tube 382, while FIG. 25C depicts the flightvehicle 380 unfolded and in flight. The air vehicle 380 can fly with aforward flight propeller 384 for forward flight and vertical flightpropellers 386 for vertical flight. The flight vehicle 380 can beconfigured to be very portable and to fit in a standard Ohio classmissile tube, with a stored width of 7 feet.

FIGS. 26A-26E depict another flight vehicle 400, with a rotatable wing402 that rotates on a pivot point 404 defining a generally vertical axisextending from the air vehicle fuselage 406. A longitudinal axis 407passes through the fuselage 406. Propellers 408 are secured to the wing402 via supports 410, 411, 413, with the middle support portion 410rotatably secured to the wingtip and capable of rotating about an axis412 passing generally wingtip-to-wingtip along the wing 402. A frontsupport portion 411 is secured to the middle support portion 410 via a(front) hinge 414, while a rear support portion 413 is secured to themiddle support portion 410 via a (rear) hinge 414. The entire flightvehicle 400 can be folded up into a compact storage configuration,possibly sized and configured to fit within a launch tube 401 asdepicted in FIGS. 26A-26B. The propeller support portions 410, 411, 413are configured to fold along several hinges 414 for storage, as depictedin FIG. 26C. For VTOL and/or STOL, the propellers can be positioned inhorizontal configuration (i.e., with essentially no forward/backward,and/or side-to-side tilt), as depicted in FIG. 26F. For forward flight,the propellers 408 can be rotated forward (by rotating the supports 410,411, 413 about the axis 412) to provide forward thrust, as depicted inFIG. 26E. A dedicated forward thrust propeller 416 may be provided.

While propellers have been discussed herein, rotors could be used insome versions of such air vehicles, such as where the air vehicles arevery large and the associated propellers (rotors) have long lengths.

Although the invention has been described in terms of particularembodiments and applications, one of ordinary skill in the art, in lightof this teaching, can generate additional embodiments and modificationswithout departing from the spirit of or exceeding the scope of theclaimed invention. For example, although the above devices and methodsare described for use in a particular manner, the devices and methodsdescribed herein could be used in a variety of different methods of use.As a further example, it will be recognized that the embodimentsdescribed above and aspects thereof may be modified, via changes inpropeller and/or engine numbers and placement, etc., to adapt aparticular situation or device to the teachings of the invention withoutdeparting from the essential scope thereof. Accordingly, it is to beunderstood that the drawings and descriptions of specific embodimentsherein are proffered by way of example to facilitate comprehension ofthe invention, and should not be construed to limit the scope thereof.

What is claimed is:
 1. An air vehicle, comprising: a fuselage having aforward axis, front, back, and sides; a first wing extending from afirst side of the fuselage; a second wing extending from a second sideof the fuselage, wherein the second side of the fuselage is opposite tothe first side of the fuselage; a first propeller support extending fromthe first wing, the first propeller support having a first propellersupport front portion and a first propeller support back portion, thefirst propeller support spaced away from the fuselage and alignedsubstantially parallel to the fuselage forward axis with the firstpropeller support front portion positioned in front of the first wingand the first propeller support back portion positioned behind the firstwing; a second propeller support extending from the second wing, thesecond propeller support having a second propeller support front portionand a second propeller support back portion, the second propellersupport spaced away from the fuselage and aligned substantially parallelto the fuselage forward axis with the second propeller support frontportion positioned in front of the second wing and the second propellersupport back portion positioned behind the second wing; a first frontVTOL propeller positioned on the first propeller support front portion,the first front VTOL propeller positioned above the first propellersupport front portion and spinning about a first front VTOL propelleraxis substantially perpendicular to the fuselage forward axis to producean airflow directed substantially perpendicular to and downward withrespect to the fuselage forward axis; a first rear VTOL propellerpositioned on the first propeller support rear portion, the first rearVTOL propeller positioned above the first propeller support rear portionand spinning about a first rear VTOL propeller axis substantiallyperpendicular to the fuselage forward axis to produce an airflowdirected substantially perpendicular to and downward with respect to thefuselage forward axis; wherein the first front VTOL propeller axis andthe first rear VTOL propeller axis define a plane therebetween whichpasses through the first wing; a second front VTOL propeller positionedon the second propeller support front portion, the second front VTOLpropeller positioned above the second propeller support front portionand spinning about a second front VTOL propeller axis substantiallyperpendicular to the fuselage forward axis to produce an airflowdirected substantially perpendicular to and downward with respect to thefuselage forward axis; a second rear VTOL propeller positioned on thesecond propeller support rear portion, the second rear VTOL propellerpositioned above the second propeller support rear portion and spinningabout a second rear VTOL propeller axis substantially perpendicular tothe fuselage forward axis to produce an airflow directed substantiallyperpendicular to and downward with respect to the fuselage forward axis;and wherein the second front VTOL propeller axis and the second rearVTOL propeller axis define a plane therebetween which passes through thesecond wing.
 2. The air vehicle of claim 1, further comprising: at leastone forward thrust propeller rotating about an axis substantiallyparallel to the fuselage forward axis, wherein the forward thrustpropeller is positioned in a plane passing vertically through thefuselage forward axis and produces an airflow substantially parallel tothe fuselage forward axis.
 3. The air vehicle of claim 2, wherein theforward thrust propeller is positioned on the back of the fuselage. 4.The air vehicle of claim 1, wherein the first front VTOL propeller,first rear VTOL propeller, second front VTOL propeller, and second rearVTOL propeller are powered by one or more electric engines.
 5. The airvehicle of claim 4, wherein the electric engines are powered bybatteries positioned in the first propeller support and in the secondpropeller support.
 6. The air vehicle of claim 4, further comprising oneor more batteries providing power to the electric engines, wherein theone or more batteries are charged by a fuel-driven engine.
 7. The airvehicle of claim 6, further comprising: at least one forward thrustpropeller rotating about an axis substantially parallel to the fuselageforward axis, wherein the forward thrust propeller is positioned in aplane passing vertically through the fuselage forward axis and producesan airflow substantially parallel to the fuselage forward axis; whereinthe fuel-driven engine drives the forward thrust propeller.
 8. A flightvehicle, comprising: a fuselage having a top, a bottom, a front, a back,and first and second sides, wherein the first side is opposite to thesecond side, the fuselage having a longitudinal axis; a wing comprisinga first wing portion extending away from the fuselage in a firstdirection and terminating at a first distal wing tip and a second wingportion extending away from the fuselage in a second direction andterminating at a second distal wing tip, wherein the first direction isopposite to the second direction; a first propeller support extendingfrom the first wing portion in a direction substantially perpendicularto a wing axis passing through the first distal wing tip and the seconddistal wing tip, the first propeller support comprising a first supportfront portion and a first support rear portion, wherein the firstpropeller support is configured to rotate the first support frontportion downward such that a distal tip of the first support frontportion moves downward with respect to the aircraft fuselage, and torotate the first support rear portion upward such that a distal tip ofthe first support rear portion moves upward with respect to the aircraftfuselage, wherein the first propeller support comprises a first supportmiddle portion, wherein the first support front portion is secured tothe first support middle portion via a first front hinge, wherein thefirst front hinge enables the first support front portion to be rotatedabout the first front hinge, and wherein the first support rear portionis secured to the first support middle portion via a first rear hinge,wherein the first rear hinge enables the first support rear portion tobe rotated about the first rear hinge; a second propeller supportextending from the second wing portion in a direction substantiallyperpendicular to the wing axis, the second propeller support comprisinga second support front portion and a second support rear portion,wherein the second propeller support is configured to rotate the secondsupport front portion downward such that a distal tip of the secondsupport front portion moves downward with respect to the aircraftfuselage, and to rotate the second support rear portion upward such thata distal tip of the second support rear portion moves upward withrespect to the aircraft fuselage, wherein the second propeller supportcomprises a second support middle portion, wherein the second supportfront portion is secured to the second support middle portion via asecond front hinge, wherein the second front hinge enables the secondsupport front portion to be rotated about the second front hinge, andwherein the second support rear portion is secured to the second supportmiddle portion via a second rear hinge, wherein the second rear hingeenables the second support rear portion to be rotated about the secondrear hinge; a plurality of propellers, comprising a first frontpropeller secured to the first support front portion, a first rearpropeller secured to the first support rear portion, a second frontpropeller secured to the second support front portion, and a second rearpropeller secured to the second support rear portion; wherein theaircraft has a first flight configuration and a second flightconfiguration; wherein the first and second support front portions arerotatable between the first flight configuration and the second flightconfiguration, and the first and second front propellers in the firstflight configuration are positioned higher with respect to the fuselagelongitudinal axis than they are in the second flight configuration;wherein the first and second support rear portions are rotatable betweenthe first flight configuration and the second flight configuration, andthe first and second rear propellers in the first flight configurationare positioned lower with respect to the fuselage longitudinal axis thanthey are in the second flight configuration.
 9. The flight vehicle ofclaim 8, wherein the first propeller support is secured to a distal endof the first wing, and the second propeller support is secured to adistal end of the second wing.
 10. The flight vehicle of claim 8,wherein the wing comprises a single rotatable wing body extending fromfirst wing tip to the second wing tip, wherein the wing is rotatablymounted to rotate about a pivot point defining a generally vertical axisextending through the fuselage.
 11. The flight vehicle of claim 8,wherein the first support front portion is secured to the first supportmiddle portion via the first front hinge such that the first supportfront portion is capable of being rotated about the first front hingeand folded alongside a leading edge of the first wing portion, andwherein the first support rear portion is secured to the first supportmiddle portion via the first rear hinge such that the first support rearportion is capable of being rotated about the first rear hinge andfolded alongside a trailing edge of the first wing portion; and whereinthe second support front portion is secured to the second support middleportion via the second front hinge such that the second support frontportion is capable of being rotated about the second front hinge to befolded alongside a leading edge of the second wing portion, and whereinthe second support rear portion is secured to the second support middleportion via the second rear hinge such that the second support rearportion is capable of being rotated about the second rear hinge to befolded alongside a trailing edge of the second wing portion.
 12. Theflight vehicle of claim 8, wherein the first flight configuration is aVTOL configuration wherein the propellers are positioned such that theyrotate to define discs passing through a plane which is substantiallyhorizontal.
 13. The flight vehicle of claim 8, further comprising: adedicated forward thrust propeller.
 14. A flight vehicle comprising: atakeoff configuration and a forward flight configuration; a fuselagehaving a forward axis, front, back, and sides; a first wing extendingfrom a first side of the fuselage; a second wing extending from a secondside of the fuselage, wherein the second side of the fuselage isopposite to the first side of the fuselage; a first front propellersecured to a distal portion of a first front propeller support movablysecured to and extending from the first wing, wherein in the takeoffconfiguration the first front propeller support extends forward from thefirst wing with the first front propeller support distal portion and thefirst front propeller positioned forward of the first wing, wherein inthe forward flight configuration the first front propeller support isrotated downward from the takeoff configuration with the first frontpropeller support distal portion and first front propeller positionedbelow the first wing; a first rear propeller secured to a distal portionof a first rear propeller support movably secured to and extending fromthe first wing, wherein in the takeoff configuration the first rearpropeller support extends rearward from the first wing with the firstrear propeller support distal portion and the first rear propellerpositioned rearward of the first wing, wherein in the forward flightconfiguration the first rear propeller support is rotated upward fromthe takeoff configuration with the first rear propeller support distalportion and first rear propeller positioned above the first wing; asecond front propeller secured to a distal portion of a second frontpropeller support movably secured to and extending from the second wing,wherein in the takeoff configuration the second front propeller supportextends forward from the second wing with the second front propellersupport distal portion and the second front propeller positioned forwardof the second wing, wherein in the forward flight configuration thesecond front propeller support is rotated downward from the takeoffconfiguration with the second front propeller support distal portion andsecond front propeller positioned below the second wing; a second rearpropeller secured to a distal portion of a second rear propeller supportmovably secured to and extending from the second wing, wherein in thetakeoff configuration the second rear propeller support extends rearwardfrom the second wing with the second rear propeller support distalportion and second rear propeller positioned rearward of the secondwing, wherein in the forward flight configuration the second rearpropeller support is rotated upward from the takeoff configuration withthe second rear propeller support distal portion and second rearpropeller positioned above the second wing.
 15. The flight vehicle ofclaim 14, wherein the first front propeller support is secured to thefirst rear propeller support via a first middle propeller support, andwherein the second front propeller support is secured to the second rearpropeller support via a second middle propeller support; wherein in thetakeoff configuration the first front propeller support, first middlepropeller support, and first rear propeller support are in linearalignment to form a first elongated structure; and wherein in thetakeoff configuration the second front propeller support, second middlepropeller support, and second rear propeller support are in linearalignment to form a second elongated structure which is parallel to thefirst elongated structure.
 16. The flight vehicle of claim 15, whereinthe first middle propeller support is rotatably secured to a distal endof the first wing, and the second middle propeller support is rotatablysecured to a distal end of the second wing.
 17. The flight vehicle ofclaim 15, wherein the first front propeller support is rotatably securedto the first middle propeller support, and the second front propellersupport is rotatably secured to the second middle propeller support. 18.The flight vehicle of claim 15, wherein the first rear propeller supportis rotatably secured to the first middle propeller support, and thesecond rear propeller support is rotatably secured to the second middlepropeller support.
 19. The flight vehicle of claim 15, wherein the firstmiddle propeller support extends from a trailing edge of the first wingto a leading edge of the first wing, and second middle propeller supportextends from a trailing edge of the second wing to a leading edge of thesecond wing.
 20. The flight vehicle of claim 14, wherein the first frontpropeller is an unshrouded propeller, the first rear propeller is anunshrouded propeller, the second front propeller is an unshroudedpropeller, and the second rear propeller is an unshrouded propeller.